| Many modern aeroelastic structures suffer from design and performance limitations caused by aeroelastic instabilities such as flutter. Existing stability augmentation techniques use controllers designed from highly simplified aerodynamic models or system ID type approaches. These approaches suffer from robustness issues caused by the low fidelity models used in design. A new approach to controller design using recent ideas from reduced order modeling (ROM) theory is introduced in this research. This approach forms high fidelity reduced order models directly from highly accurate, large order, parallel nonlinear aeroelastic computational simulations. The resulting ROMs are then used as a basis for the controller design problem. This model reduction approach is developed and implemented on high order aeroelastic models of a 1D piston, a 2D NACA0012 airfoil with trailing edge flap, and a 3D AGARD wing with trailing edge flap. The model reduction approach is also compared to other existing ROM techniques. Controllers based on the ROMs are used to show the robustness of the controlled system exposed to a wide variety of flight conditions. |
